EP3012337B1 - Heissgeschmiedete ti-al-legierung und verfahren zur herstellung davon - Google Patents

Heissgeschmiedete ti-al-legierung und verfahren zur herstellung davon Download PDF

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Publication number
EP3012337B1
EP3012337B1 EP14814461.1A EP14814461A EP3012337B1 EP 3012337 B1 EP3012337 B1 EP 3012337B1 EP 14814461 A EP14814461 A EP 14814461A EP 3012337 B1 EP3012337 B1 EP 3012337B1
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Prior art keywords
phase
tial
hot
alloy
atom
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EP14814461.1A
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English (en)
French (fr)
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EP3012337A1 (de
EP3012337A4 (de
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Toshimitsu Tetsui
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National Institute for Materials Science
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National Institute for Materials Science
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Priority claimed from JP2013128866A external-priority patent/JP6202556B2/ja
Priority claimed from JP2014029044A external-priority patent/JP2015151612A/ja
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Publication of EP3012337A1 publication Critical patent/EP3012337A1/de
Publication of EP3012337A4 publication Critical patent/EP3012337A4/de
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the present invention relates to a TiAl-based alloy to be suitably used for a rotor blade of a gas turbine for power generation, a gas turbine for aircraft, or the like, and specifically, to a hot-forged TiAl-based alloy in which hot forgeability is excellent, strength is high at a high temperature, and ductility is also excellent in a room temperature.
  • the present invention relates to a method for producing the hot-forged TiAl-based alloy.
  • This TiAl-based alloy is an alloy composed mainly of TiAl or Ti 3 Al, which is an intermetallic compound having excellent high-temperature strength, and the alloy is excellent in heat resistance as described above.
  • the TiAl alloy which is a lightweight heat resistance alloy, is used as a casting material and a forged material.
  • the casting material has a perfect lamellar structure laminated with a ⁇ 2-phase and a ⁇ -phase which are excellent in high-temperature strength, but there is a problem that room-temperature ductility is deficient because forgeability is poor and a crystal grain is coarsened. Therefore, for example, a technique is proposed in Patent Literatures 1 and 2, in which a TiAl-based alloy material as a hot forging material having a predetermined composition is held in an equilibrium temperature range of ( ⁇ + ⁇ )-phase and is then subjected to plastic working, thereby eliminating casting defects and fining a structure by a synergistic effect of working distortion and phase transformation.
  • the hot-forged TiAl-based alloy material is held in an equilibrium temperature range of ( ⁇ + ⁇ )-phase, ( ⁇ + ⁇ + ⁇ )-phase, or ( ⁇ + ⁇ )-phase, an area fraction of lamella grain and ⁇ -phase or a grain size of the lamella grain is controlled, and thus the TiAl-based alloy having excellent machinability and high-temperature strength can be produced.
  • a hot working method other than the hot forging for example, extrusion or rolling-type forging can be used.
  • the case of the casting material described above was not sufficient in view of a general coarseness of the cast structure and improvement in ductility at a room temperature.
  • foreign matter such as sludge may collide with the rotor blade at the time of operation, or at the time of production of the rotor blade, the blade may be broken due to impact at the time of fixing the blade to an outer periphery of the disk with a hammer.
  • isothermal forging is also commonly used as a forging method of the forged material of the TiAl-based alloy, the isothermal forging being characterized in that the mold and the material are held together at a high temperature and are slowly deformed at a constant temperature.
  • process costs are very expensive and production of large parts can be difficult because of the limitation of methodology that the mold and the material are heated together.
  • a ⁇ -phase having excellent high temperature deformability (that is, small high-temperature strength) is generated by the addition of a ⁇ -stabilization element (Mn, V, Nb, Cr, or the like), and thus so-called hot forging can be performed to cause high-speed deformation as a temperature decreases during the forging.
  • a ⁇ -stabilization element Mn, V, Nb, Cr, or the like
  • JP 06340955 describes a TiAl-based alloy comprising 38-53 atom % Al, with ⁇ 5% of the Ti substituted by at least one of Mo, V, Mn, Cr, Nb, W and Si.
  • US-6051084 describes TiAl alloys containing Nb and Cr.
  • the present invention has been made to solve the above problems in the TiAl-based alloy and an object thereof is to provide a TiAl-based alloy which is excellent in hot forgeability as a hot forging material, ductility at a room temperature, and impact properties as well as having excellent high-temperature strength.
  • the present invention provides the TiAl-based alloy of claim 1.
  • the invention also provides the method for producing this TiAl-based alloy as defined by claim 2.
  • the invention also provides a rotor blade for turbine that uses the TiAl-based alloy material produced in such a manner that an ingot having the composition according to the invention is produced by the production method of the invention, and also provides a turbine that uses said rotor blade.
  • a TiAl-based alloy which is excellent in hot forgeability as a hot forging material, ductility at a room temperature, and impact properties as well as having excellent high-temperature strength.
  • a TiAl-based alloy according to an embodiment of the invention consists of: 41 to 45 atom% of Al, 7 to 9 atom% of Nb, 0.4 to 4.0 atom% of Cr, 0.3 to 1.0 atom% of Si, and 0.3 to 1.0 atom% of C, and the balance Ti with inevitable impurities.
  • the other, optional, aspect of the TiAl-based alloy according to the embodiment of the present invention is a TiAl-based alloy in which at least one element selected from the group consisting of W, Mo, B, Hf, Ta, and Zr is further contained in the above TiAl-based alloy to be 0.1 to 3 atom% in total.
  • an ingot is prepared by dissolution, a process in which the ingot is held at a coexisting temperature range of a hexagonal close-packed structure phase ( ⁇ -phase) and a body-centered cubic structure phase ( ⁇ -phase) and is then subjected to hot forging, and a process in which the hot-forged TiAl-based alloy material is held in a temperature range of from 1230°C to 1290°C, which is an ⁇ -single phase region, for 1 to 20 hours and is then subjected to a cooling treatment at a rate of from 1 [°C/min.] to 10 [°C/min.].
  • the hexagonal close-packed structure phase ( ⁇ -phase) is transformed into an eutectoid phase of the hexagonal close-packed structure phase ( ⁇ -phase) and the TiAl phase (y-phase), and is further transformed into an eutectoid phase of the Ti 3 Al phase ( ⁇ 2-phase) and the TiAl phase ( ⁇ -phase).
  • a rotor blade for turbine of the present invention is characterized in that the TiAl-based alloy having the above composition is produced by the production method described above.
  • a gas turbine for power generation, a gas turbine for aircraft, a turbocharger for ship, or a gas turbine or a steam turbine for various industrial machines according to the invention is characterized by using the rotor blade for turbine.
  • Aluminum (Al) When the content of Al is in the range of from 41.0 atom% to 45.0 atom%, it is preferred because the ⁇ -phase does not exist in a final state after the heat treatment, a perfect lamellar structure laminated with the ⁇ 2-phase and the ⁇ -phase is obtained, and the hot forgeability is excellent.
  • the excellence in the hot forgeability means that large cracks do not occur even when the hot forging is performed under conditions illustrated in Figs. 1(A) and 1(C) in particular and fine cracks caused by the change in surface structure of oxidation or the like are not included.
  • the content of Al is less than 41.0 atom%, the hot forgeability is good, but the ratio of the ⁇ 2-phase becomes too high. Thus, in this case, the ductility may be deteriorated.
  • the hot forgeability When the content of Al exceeds 45.0 atom%, the hot forgeability may become poor.
  • Niobium (Nb) When the content of Nb is in the range of from 7.0 atom% to 9.0 atom%, it is preferred because oxidation resistance is improved. When the content of Nb is less than 7.0 atom%, the effect of improving the oxidation resistance may be insufficient. The content of Nb exceeds 9.0 atom%, problems may arise in that the ⁇ -phase remains and the weight increases.
  • Chromium (Cr) When the content of Cr is in the range of from 0.4 atom% to 4.0 atom%, it is preferred because the hot forgeability is improved. When the content of Cr is less than 0.4 atom%, for example, as indicated in alloys 10 and 23 to be described below, the hot forgeability may be deteriorated. When the content of Cr exceeds 4.0 atom%, the ⁇ -phase remains, and the high-temperature strength such as creep strength may be deteriorated.
  • Si Silicon (Si): When the content of Si is in the range of from 0.3 atom% to 1.0 atom%, it is preferred because the creep strength is improved. When the content of Si is less than 0.3 atom%, for example, as indicated in an alloy 21 to be described below, the creep strength may not be improved. When the content of Si exceeds 1.0 atom%, the hot forgeability may become poor.
  • the alloy element parameter P is less than 1.1 atom%, the hot forgeability may become poor.
  • the alloy element parameter P exceeds 2.3 atom%, since the ⁇ -phase remains even after the heat treatment, the high-temperature strength such as creep strength is deteriorated and thus an available temperature may be lowered.
  • the crystal grain size of the lamella grain is preferably 1 ⁇ m or more and 200 ⁇ m or less, and particularly preferably 30 ⁇ m or more and 100 ⁇ m or less.
  • the crystal grain size of the lamella grain is 100 ⁇ m or less, it is preferred because the room-temperature ductility is ensured. It is industrially very difficult to make the average grain size of the lamella grain to be less than 1 ⁇ m, and when the average grain size of the lamella grain is less than 30 ⁇ m, production costs may increase or production yield may be reduced. On the other hand, when average grain size exceeds 200 ⁇ m, the room-temperature ductility, especially, impact properties may be reduced.
  • the temperature range in which the hot-forged TiAl-based alloy is held in the equilibrium temperature range of the ⁇ -single phase region is preferably from 1230°C to 1290°C.
  • the temperature range is lower than 1230°C, since it is within the ( ⁇ + ⁇ ) region, the perfect lamellar structure may not be formed after cooling.
  • the temperature range exceeds 1290°C, since it is within the ( ⁇ + ⁇ ) region, the ⁇ -phase may remain by the cooling rate after the cooling.
  • the time at which the hot-forged TiAl-based alloy material is held within the equilibrium temperature range of the ⁇ -single phase region is preferably from one hour to 20 hours.
  • the holding time is shorter than one hour, the time is too short and thus the ⁇ -single phase may not be obtained.
  • the holding time exceeds 20 hours the time is too long and thus the crystal grain size of the ⁇ -grain (final lamella grain) is coarsened, whereby the ductility or the like may be deteriorated.
  • the cooling rate after the hot-forged TiAl-based alloy material is held for a predetermined holding time within the equilibrium temperature range of the ⁇ -single phase region is preferably from 1 [°C/min.] to 10 [°C/min.].
  • the cooling rate is slower than 1 [°C/min.] since the cooling rate is too slow and the gap between the ⁇ 2-phase and the ⁇ -phase within the lamella grain becomes coarse, the high-temperature strength such as creep strength may be deteriorated.
  • the cooling rate exceeds 10 [°C/min.] since the cooling rate is too fast and the ratio of the ⁇ 2-phase is too large, the ductility may be deteriorated.
  • the method for producing the TiAl-based alloy according to the embodiment of the present invention is as follows. First, the ingot having the composition described above is melted. Subsequently, the ingot is subjected to hot forging. That is, similarly with the conventional hot-forged TiAl alloy, after being held in an coexisting region of the ⁇ -phase and the ⁇ -phase, the ingot is taken out of the furnace and is subjected to the hot forging for working at a high strain rate while being rapidly cooled. In this case, similarly with the hot forged material of the conventional TiAl-based alloy, the hot forgeability can be ensured due to the effect that the ⁇ -phase rich in plastic deformability exists. In addition, due to the effect that plastic strain is imparted by the hot forging, the crystal grain size becomes finer.
  • the hot-forged material is subjected to a heat treatment.
  • the material is held for a predetermined time at the ⁇ -single phase region, and thus the ⁇ -phase existing in the forged material is eliminated and the ⁇ -single phase is obtained.
  • transformation of ⁇ ⁇ ⁇ + ⁇ ⁇ ⁇ 2+ ⁇ occurs.
  • the crystal grain is not coarsened by optimization of the holding time at the ⁇ -region, and it is possible to obtain a perfect lamellar structure laminated with the ⁇ 2-phase and the ⁇ -phase, which are fine grains and are finally excellent in high-temperature strength and room-temperature ductility, by optimization of the cooling rate.
  • the alloy of the present invention is characterized by not including the ⁇ -phase in the final state.
  • Figs. 1(A) to 17 relate to an embodiment of the present invention.
  • Figs. 1(A) to 1(C) illustrate an ingot used in Example and a hot forging test for evaluating hot forgeability;
  • Fig. 1(A) illustrates an appearance photograph of the ingot and a cutting position (using a lower side) of a material subjected to a forging test,
  • Fig. 1(B) is a circumstantial photograph during the hot forging test, and
  • Fig. 1(C) is an explanatory view of a change of height in the hot forging test.
  • Fig. 1(A) is a representative example of the appearance of the ingot prepared by alloy compositions illustrated in Figs. 2 and 3 . All of the ingots have almost the same appearance.
  • Figs. 2 and 3 are diagrams illustrating compositions of trial ingots and summaries of evaluation test results of the trial ingots.
  • the ingot is prepared by high-frequency melting using an yttria crucible.
  • a raw material of the ingot includes sponge Ti, granular raw materials of Al, Nb, Cr, and Si, and C added in the form of a TiC powder, and the total weight is about 700 g.
  • a melting atmosphere is in argon gas.
  • Casting was performed using a cast iron mold having an inner diameter of ⁇ 40 mm, cutting is performed at the position illustrated in Fig. 1(A) , and the lower side is subjected to the hot forging test.
  • the weight of the ingot in the photograph was about 700 g, but the weight of the ingot after riser cutting was about 450 g.
  • the hot forging test was performed in the same manner as the circumstantial photograph illustrated in Fig. 1(B) and the explanatory view illustrated in Fig. 1(C) . That is, the heating temperature was 1350°C, the ingot was taken out of the furnace and was placed in a press, and forging was performed by descending of the press. The descending speed of the press was 50 mm/second or faster, the forging direction was upset, and the number of times of the forging was seven times. The material returned to the furnace every each forging and was subjected to reheating. In the hot forging test, the height was changed into 90 mm (initial height of the ingot), 80 mm, 70 mm, 55 mm, 40 mm, 30 mm, 20 mm, and 15 mm, and compression was performed in this order.
  • the hot-forged test material was subjected to an annealing treatment for cooling at 0.2°C/min., and cross-sectional structure thereof was observed by a reflected electron image of the scanning electron microscope, whereby the presence or absence of the ⁇ -phase remaining was investigated.
  • This heat treatment was intended to investigate whether the ⁇ -phase was ultimately stabilized in each composition of Figs. 2 and 3 , and thus the annealing treatment was performed for the purpose.
  • this heat treatment is independent of heat treatment conditions after the forging which is a requirement of the present invention.
  • the hot forged material after the above procedure 3 was subjected to a heat treatment test by changing of the following conditions, and appropriate heat treatment conditions were investigated from structure observation.
  • the changed conditions include a holding temperature, a holding time, and a cooling rate.
  • the temperature range of the holding temperature for holding the alloy in an equilibrium temperature range of ⁇ -single phase region was preferably 1230 to 1290°C.
  • the holding time was a time for holding the hot-forged TiAl-based alloy within the equilibrium temperature range of the ⁇ -single phase region and was preferably 1 to 20 hours.
  • the cooling rate was a cooling rate of the alloy after the hot-forged TiAl-based alloy was held in the equilibrium temperature range of the ⁇ -single phase region for a predetermined time, and was preferably 1 to 10 [°C/min.].
  • an appropriate structure is determined as follows. That is, an object of structure is a fine structure in which lamella grains are densely arranged, the lamella grains being alternately laminated with an ⁇ 2-phase of gray in the reflected electron image and a ⁇ -phase of black in the reflected electron image and having an average grain size of 1 to 200 ⁇ m.
  • a ⁇ -phase of white in the reflected electron image or a ⁇ -grain in which the equi-axied ⁇ -phase of black in the reflected electron image is largely grown is not included.
  • Silicide of a small white granular shape in the reflected electron image is outside the scope of the evaluation determination, the silicide being precipitated along with the addition of Si.
  • each plot corresponds to a separate ingot having a different composition, and a state of crack occurrence in the hot forging is indicated by a black-plotted mark or a void-plotted mark.
  • the crack occurs in the case of the ingot having a composition of the black-plotted mark, and the crack does not occur in the case of the ingot having a composition of the void-potted mark.
  • An ingot having a composition in which the alloy element parameter P is 1.1 atom% or less and the area ratio of the ⁇ -phase of the material which is water-cooled in the condition of 1350°C ⁇ 1 h is 30% or less has poor hot forgeability.
  • an ingot having a composition in which the alloy element parameter P is 1.1 atom% or more and the area ratio of the ⁇ -phase of the material which is water-cooled in the condition of 1350°C ⁇ 1 h is 30% or more has excellent hot forgeability.
  • the relation between the presence or absence of the ⁇ -phase residue and the alloy element parameter P and the relation between the presence or absence of the ⁇ -phase residue and the area ratio of the ⁇ -phase of a material, which is water-cooled in the condition of 1350°C ⁇ 1 h, are as follows.
  • the ⁇ is eliminated after the annealing treatment. That is, in this composition, the ⁇ -phase is finally unstable.
  • Fig. 6 is an appearance photograph when an ingot (alloy 13 having a composition of Ti-42Al-8Nb-2.3Cr-0.9Si-0.7C (atom%)) according to the embodiment of the present invention is subjected to the hot forging at 1350°C. Since it is estimated that the amount of ⁇ -phase at 1350°C is 42% much larger than that in the evaluation in the procedure 2, forgeability is good, and no crack occurs.
  • Fig. 7 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is heat-treated under appropriate conditions after being subjected to the hot forging.
  • the appropriate conditions refer to the heat-treatment conditions described above.
  • the ⁇ -phase existing in the hot forged material is no longer present in the alloy, the ⁇ -phase having excellent high temperature deformability (low high-temperature strength).
  • the grain size is slightly coarsened compared to that of the forged alloy, but becomes significantly smaller than that of a casting material. Therefore, since this hot forged material has the above structure, it is excellent in both of the high-temperature strength and the room-temperature ductility.
  • Fig. 8 is an appearance photograph when an ingot (composition: Ti-41AI-7Nb-0.9Si-0.4C (atom%)) of Comparative Alloy 6 is subjected to the hot forging at 1350°C. Since it is estimated that the amount of ⁇ -phase at 1350°C is 12% smaller than that in the evaluation in the procedure 2, deformability is poor, and large cracks have occurred.
  • Fig. 9 is a photograph of a reflected electron image structure of a test material obtained in such a manner that the forged TiAl material of Comparative Alloy 6 is heat-treated under appropriate conditions. Similarly to the inventive alloy, a perfect lamellar structure having no ⁇ -phase (large white phase) appears in the photograph. Fine white points indicate precipitates (silicide) caused by Si.
  • Fig. 10 is an appearance photograph when an ingot (composition: Ti-40AI-7Nb-3Cr-0.6Si-0.9C (atom%)) of Comparative Alloy 4 is subjected to the hot forging at 1350°C. Since it is estimated that the amount of ⁇ -phase at 1350°C is 63% much larger than that in the evaluation in the procedure 2, forgeability is good, and no crack occurs.
  • Fig. 11 is a photograph of a reflected electron image structure of a test material obtained in such a manner that the ingot of Comparative Alloy 4 is heat-treated under appropriate conditions after being subjected to the hot forging. Since a ⁇ -phase (large white phase) having excellent high temperature deformability (low high-temperature strength) remains, it is assumed that the high-temperature strength is low. In fact, a creep rupture time (h) in a state of 870°C ⁇ 225 MPa is 16 hours which is shorter than that in the inventive alloy.
  • Fig. 12 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is held at 1220°C lower than the appropriate holding temperature in a heat treatment after being subjected to the hot forging.
  • Other heat treatment conditions are appropriate conditions. It is found that a large black equi-axied ⁇ -phase exists. That is, since a perfect lamellar structure is not formed, it is considered that the high-temperature strength is lower than that of the inventive alloy. This is considered because the holding temperature of 1220°C is within a ( ⁇ + ⁇ ) region rather than an ⁇ -single phase region.
  • Fig. 13 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is held at 1300°C higher than the appropriate holding temperature in a heat treatment after being subjected to the hot forging. Other heat treatment conditions are appropriate conditions. It is found that a large white ⁇ -phase exists. Since the ⁇ -phase remains, it is considered that the high-temperature strength is lower than that of the inventive alloy. This is considered because the holding temperature of 1300°C is within a ( ⁇ + ⁇ ) region rather than an ⁇ -single phase region.
  • Fig. 14 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is held for 0.5 hours shorter than the appropriate holding time in a heat treatment after being subjected to the hot forging. Other heat treatment conditions are appropriate conditions. It is found that a large white ⁇ -phase exists. Since the ⁇ -phase remains, it is considered that the high-temperature strength is lower than that of the inventive alloy. This is considered because the holding time is short and thus a sufficient time for transformation of the ⁇ -phase existing in the forged material into the ⁇ -phase is not left.
  • Fig. 15 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is held for 23 hours longer than the appropriate holding time in a heat treatment after being subjected to the hot forging.
  • Other heat treatment conditions are appropriate conditions. It is found that a perfect lamellar structure is formed, but a crystal grain is large. Since the crystal grain is large, it is considered that the room-temperature ductility or the like is lower than that of the inventive alloy. This is considered because the holding time is long and thus an ⁇ -grain (lamellar grain after cooling) is coarsened during the holding.
  • Fig. 16 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is cooled at 0.7 [°C/min.] slower than the appropriate cooling rate in a heat treatment after being subjected to the hot forging.
  • Other heat treatment conditions are appropriate conditions. It is found that a perfect lamellar structure is formed, but a lamella gap is large. Since the lamella gap is large, it is considered that the high-temperature strength is lower than that of the inventive alloy.
  • Fig. 17 is a reflected electron image photograph of a test material obtained in such a manner that the ingot (alloy 13) according to the embodiment of the present invention is cooled at 15 [°C/min.] faster than the appropriate cooling rate in a heat treatment after being subjected to the hot forging.
  • Other heat treatment conditions are appropriate conditions. It is found that a perfect lamellar structure is formed, but a lamella gap is small. Since the lamella gap is small, it is considered that the room-temperature ductility or the like is lower than that of the inventive alloy.
  • the above embodiments are merely made to describe in detail the present invention. Accordingly, the present invention should not be restrictively construed with the above embodiments.
  • the TiAl-based alloy of the present invention or the method for producing the TiAl-based alloy includes ratio changes of composition elements within an obvious range in a person skilled in the art, for example, composition changes in an allowable range included inevitably in manufacturing or composition changes in an allowable range depending on variations in purchase price or fluctuations in supply state of raw-material compositions.
  • the TiAl-based alloy according to the present invention is excellent in high-temperature strength or impact resistance, and thus is suitably used for a rotor blade of a gas turbine or steam turbine for power generation, aircraft, ship, or various industrial machines.
  • the TiAl-based alloy material produced by the present invention is excellent in high-temperature strength and has excellent ductility or impact properties.
  • this material is used for the rotor blade of various turbines or turbocharger, it is possible to improve energy efficiency due to an increase in an engine speed and contribute to reduction in weight while maintaining reliability.
  • the TiAl-based alloy according to the present invention can be used to manufacture large parts from excellent hot forgeability and is suitably used for the rotor blade or a disk of an aircraft engine or the gas turbine for power generation because of being excellent in high-temperature strength, room-temperature ductility, or the like.
  • the TiAl-based alloy according to the present invention it is possible to obtain a large-scaled material which is excellent in high-temperature strength and room-temperature ductility. Since the rotor blade or disk made of this material has excellent high-temperature strength or room-temperature ductility, when this material is used for the rotor blade of the aircraft engine or the gas turbine for power generation, it is possible to improve energy efficiency due to an increase in an engine speed and an increase in size of parts while maintaining reliability.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
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Claims (4)

  1. Legierung auf der Basis von TiAl, bestehend aus:
    Al: 41 bis 45 Atom-%,
    Nb: 7 bis 9 Atom-%,
    Cr: 0,4 bis 4,0 Atom-%,
    Si: 0,3 bis 1,0 Atom-% und
    C: 0,3 bis 1,0 Atom-%,
    und wahlweise 0,1 bis 3 Atom-% mindestens eines Elements ausgewählt aus der Gruppe bestehend aus W, Mo, B, Hf, Ta und Zr, wobei der Rest aus Ti und unvermeidlichen Verunreinigungen besteht,
    wobei ein Legierungselementparameter P, der durch die folgende Formel erhalten wird, im Zusammensetzungsbereich von 1,1 bis 2,3 liegt; P = 41 − Al / 3 + 0,25 Nb + 0,8 Cr − 0,8 Si − 1,7 C
    Figure imgb0003
     und
    die Legierung auf der Basis von TiAl eine feine Struktur aufweist, in der Lamellenkörner, die abwechseln mit einer Ti3Al-Phase (α2-Phase) und einer TiAl-Phase (γ-Phase) laminiert sind, dicht angeordnet sind und eine ß-Phase nicht eingeschlossen ist, wobei die Lamellenkörner eine durchschnittliche Korngröße von 1 bis 200 µm aufweisen.
  2. Verfahren für die Herstellung einer Legierung auf der Basis von TiAl, umfassend:
    ein Verfahren, bei dem die Legierung auf der Basis von TiAl nach Anspruch 1 in einem koexistierenden Temperaturbereich einer Phase hexagonaler enggepackter Struktur (α-Phase) und einer Phase körperzentrierter kubischer Struktur (ß-Phase) gehalten wird und dann Warmschmieden unterworfen wird; und
    ein Verfahren, bei dem das warmgeschmiedete Legierungsmaterial auf der Basis von TiAl in einem Temperaturbereich von 1230 °C bis 1290 °C 1 bis 20 Stunden lang gehalten und dann einer Kühlbehandlung mit einer Rate von 1 [°C/min] bis 10 [°C/min] unterworfen wird.
  3. Rotorflügel für eine Turbine, bei dem das Legierungsmaterial auf der Basis von TiAl verwendet wird, das derart hergestellt wird, dass ein Barren, der eine Zusammensetzung nach Anspruch 1 aufweist, durch das Herstellungsverfahren nach Anspruch 2 hergestellt wird.
  4. Turbine, bei der der Rotorflügel für Turbinen nach Anspruch 3 verwendet wird.
EP14814461.1A 2013-06-19 2014-06-02 Heissgeschmiedete ti-al-legierung und verfahren zur herstellung davon Not-in-force EP3012337B1 (de)

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PCT/JP2014/064611 WO2014203714A1 (ja) 2013-06-19 2014-06-02 熱間鍛造型ＴｉＡｌ基合金およびその製造方法

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DE102015103422B3 (de) 2015-03-09 2016-07-14 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
CN104928531B (zh) * 2015-05-12 2017-03-01 哈尔滨工业大学 一种均匀化TiAl合金层片组织及其制备方法
WO2017123186A1 (en) * 2016-01-11 2017-07-20 General Electric Company Tial-based alloys having improved creep strength by strengthening of gamma phase
EP3508594B8 (de) 2016-09-02 2021-06-16 IHI Corporation Tial-legierung und verfahren zur herstellung davon
US11920219B2 (en) 2018-12-21 2024-03-05 National Institute For Materials Science Hot-forged tial-based alloy, method for producing same, and uses for same
CN111326220B (zh) * 2020-04-16 2023-08-15 重庆大学 一种高强韧锆钛基合金的设计方法
CN111826536A (zh) * 2020-06-03 2020-10-27 周睿之 一种用于金刚石锯片的钛合金基体制备方法
CN113958409B (zh) * 2020-07-21 2023-02-24 中国航发商用航空发动机有限责任公司 一种航空钛合金部件及其制备方法
CN115386780B (zh) * 2022-09-13 2023-03-21 南京工业大学 一种轻质高强高韧高熵超合金及其制备方法

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